Takeoff and landing control using force sensor by electrically-powered helicopters

Masanori Fujita, Akira Shimada

Research output: Contribution to journalArticle

4 Citations (Scopus)

Abstract

This paper introduces a takeoff and landing control technique related to a helicopter. The presented control system consists of a small toy electrically-powered helicopter for indoor flights, a flight base under which a focre sensor is set, and a helicopter control terminal which is connected to a system controller. The force sensor use is intended to realize soft takeoff and landing control. When the helicopter stands on the base, the force sensor outputs lift force data corresponding to the weight of the helicopter. As the operational voltage rises, the helicopter almost takes off from the base. Concurrently, the forse sensor output closes to 0. Thus, if the system controller controls the voltage arbitrarily, it is expected to realize the soft takeoff and landing control. This paper introduces the design process including modeling based on ststem identification technique, and shows the simulation and experimental results of the lift force control.

Original languageEnglish
Pages (from-to)112-117
Number of pages6
JournalIEEJ Transactions on Industry Applications
Volume127
Issue number2
DOIs
Publication statusPublished - 2007
Externally publishedYes

Fingerprint

Force control
Takeoff
Landing
Helicopters
Sensors
Controllers
Electric potential
Control systems

Keywords

  • Control
  • Disturbance observer
  • Force sensor
  • Helicopter
  • System identification
  • Takeoff and landing

ASJC Scopus subject areas

  • Electrical and Electronic Engineering
  • Industrial and Manufacturing Engineering

Cite this

Takeoff and landing control using force sensor by electrically-powered helicopters. / Fujita, Masanori; Shimada, Akira.

In: IEEJ Transactions on Industry Applications, Vol. 127, No. 2, 2007, p. 112-117.

Research output: Contribution to journalArticle

@article{c22b7eaa80094afc9615bc4ce3a7ca59,
title = "Takeoff and landing control using force sensor by electrically-powered helicopters",
abstract = "This paper introduces a takeoff and landing control technique related to a helicopter. The presented control system consists of a small toy electrically-powered helicopter for indoor flights, a flight base under which a focre sensor is set, and a helicopter control terminal which is connected to a system controller. The force sensor use is intended to realize soft takeoff and landing control. When the helicopter stands on the base, the force sensor outputs lift force data corresponding to the weight of the helicopter. As the operational voltage rises, the helicopter almost takes off from the base. Concurrently, the forse sensor output closes to 0. Thus, if the system controller controls the voltage arbitrarily, it is expected to realize the soft takeoff and landing control. This paper introduces the design process including modeling based on ststem identification technique, and shows the simulation and experimental results of the lift force control.",
keywords = "Control, Disturbance observer, Force sensor, Helicopter, System identification, Takeoff and landing",
author = "Masanori Fujita and Akira Shimada",
year = "2007",
doi = "10.1541/ieejias.127.112",
language = "English",
volume = "127",
pages = "112--117",
journal = "IEEJ Transactions on Industry Applications",
issn = "0913-6339",
publisher = "The Institute of Electrical Engineers of Japan",
number = "2",

}

TY - JOUR

T1 - Takeoff and landing control using force sensor by electrically-powered helicopters

AU - Fujita, Masanori

AU - Shimada, Akira

PY - 2007

Y1 - 2007

N2 - This paper introduces a takeoff and landing control technique related to a helicopter. The presented control system consists of a small toy electrically-powered helicopter for indoor flights, a flight base under which a focre sensor is set, and a helicopter control terminal which is connected to a system controller. The force sensor use is intended to realize soft takeoff and landing control. When the helicopter stands on the base, the force sensor outputs lift force data corresponding to the weight of the helicopter. As the operational voltage rises, the helicopter almost takes off from the base. Concurrently, the forse sensor output closes to 0. Thus, if the system controller controls the voltage arbitrarily, it is expected to realize the soft takeoff and landing control. This paper introduces the design process including modeling based on ststem identification technique, and shows the simulation and experimental results of the lift force control.

AB - This paper introduces a takeoff and landing control technique related to a helicopter. The presented control system consists of a small toy electrically-powered helicopter for indoor flights, a flight base under which a focre sensor is set, and a helicopter control terminal which is connected to a system controller. The force sensor use is intended to realize soft takeoff and landing control. When the helicopter stands on the base, the force sensor outputs lift force data corresponding to the weight of the helicopter. As the operational voltage rises, the helicopter almost takes off from the base. Concurrently, the forse sensor output closes to 0. Thus, if the system controller controls the voltage arbitrarily, it is expected to realize the soft takeoff and landing control. This paper introduces the design process including modeling based on ststem identification technique, and shows the simulation and experimental results of the lift force control.

KW - Control

KW - Disturbance observer

KW - Force sensor

KW - Helicopter

KW - System identification

KW - Takeoff and landing

UR - http://www.scopus.com/inward/record.url?scp=33847723350&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=33847723350&partnerID=8YFLogxK

U2 - 10.1541/ieejias.127.112

DO - 10.1541/ieejias.127.112

M3 - Article

VL - 127

SP - 112

EP - 117

JO - IEEJ Transactions on Industry Applications

JF - IEEJ Transactions on Industry Applications

SN - 0913-6339

IS - 2

ER -